Finite Element Analysis of Carbon Fibre Reinforced Aircraft Wing
|
|
- Myles Miller
- 6 years ago
- Views:
Transcription
1 IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: ,p-ISSN: X, Volume 11, Issue 4 Ver. V (Jul- Aug. 2014), PP Finite Element Analysis of Carbon Fibre Reinforced Aircraft Wing Kirankumar Reddy 1, Sunil Manganshetty 2 1 M.Tech Scholar, Mechanical Engineering Dept., PDA College of Engineering, Gulbarga, India 2 Professor, Mechanical Engineering Dept., PDA College of Engineering, Gulbarga, India Abstract: Subsonic aircraft is used as business jets and commercial airplanes. The wings are usually straight or with low sweep angle. The main group of materials used in aircraft construction has been wood, steel, aluminum alloys and more recently, titanium alloys and fiber reinforced composites. Several factors influence the selection of material of which strength allied to lightness is the most important. Composite materials are well known for their excellent combination of high structural stiffness and low weight.cfc is seen to have a modulus twice &strength three times that of aluminum alloy, the conventional material used in aircraft construction. In the present work the aircraft wing components skin is analyzed considering both isotropic and composite materials. The parametric study conducted using MSc Nastran finite element package. From the studies conducted regarding the weight reduction, it is estimated that replacement of Al. alloy by CFC results in 52.96% saving in the total structural weight of the aircraft wing. Keywords: CFC, Finite Element Model, ply orientation, Skin, Static Analysis, Subsonic wing. I. Introduction For aerodynamic reasons, the wing cross-section must have a streamlined shape commonly referred to as an airfoil section. The aerodynamic forces in flight change in magnitude, direction and location. Likewise in the various landing operations the loads change in magnitude, direction and location, thus the required structure must be one that can efficiently resist loads causing combined tension, com-press ion, bending and torsion. To provide tensional resistance, a portion of the airfoil surface ribs be covered with a metal skin and then adding one or more internal metal webs to produce a single closed cell or a multiple call wing cross-section. The external skin surface which is relatively thin for subsonic aircraft is efficient for resisting tensional shear stresses and tension, but quite inefficient in resisting compressive stresses due to bending of wing. To provide strength efficiency, span-wise stiffening units commonly referred to as flange stringers are attached to the inside of the surface skin. To hold the skin surface to airfoil shape and to provide a medium for transferring surface air pressures to the cellular beam structure, chord wise formers and rids are added. To transfer large concentrated loads into the cellular beam structure, heavy ribs, commonly referred to as bulkheads, are used. In this work the wing optimized by conducting several iterations for the spars, ribs, wing skin. In each iteration the sizing of the done at the final iteration the optimized obtained still there is a scope for reducing weight for replacing the metallic wing skin by composite. The composite wing skin is analyzed for the required straight consideration. There is a considerable reduction in the weight of 52.96% in the wing by top and bottom skin Most of the aircraft produced are subsonic aircrafts Which are designed to fly below Mach 0.8 small light weight airplanes have lower Mach number which is around mach0.2.business jets and commercial airlines can fly at maximum speeds up to mach0.85.light subsonic aircrafts use piston engines as the power plant while business jets and commercial airlines use turboprop or by pass turbofan. Structurally the loading on the air frame varies from plane to plane. The wings are usually straight or with low sweep angle. Typically speeds for subsonic aircrafts are less than610 mph and Mach number M 1<0.8.It flies below the speed of sound. II. Materials And Method 2.1 Configuration of Subsonic Aircraft Wing The wing of subsonic aircraft considered in the present study is rectangular taper wing. The cross section of the wing is aero foil. The wing has a root chord of 1500mm and tip chord of 650mm.The various structural components of a subsonic aircraft wing structure considered are: Panels-Top and Bottom skin. Spars-Front and Rear spar. Ribs-Root rib, Ribs1, 2, 3,4,5,6 and Tip Rib The air loads act directly on the wing cover, which transmits the loads to the ribs. The ribs transmit the loads to the spar webs and distribute the load between them in proportion to the web stiffness. The use of several spars permit a reduction in rib stresses and also provides a better support for the span wise bending 12 Page
2 Ribs are used to hold the panel to contour shape. The rib also has another major purpose, to transfer or distribute the loads. The ribs provide stability to spars and panels. The primary function of the wing skin is to form an impermeable surface for supporting the aerodynamic pressure distribution from which the lifting capability of the wing is derived 2.2 Structural Layout The front spar of aircraft wing is placed about 15% of the wing chord and longitudinal axis to facilitate mounting of leading edge and provide space for accommodating landing gear.the rear spar of aircraft wing is placed about 68% of wing chord to facilitate mounting of control surfaces. The rear spar is oriented normal to the fuselage axis for better load transfer.seven ribs are connected to the spars to form the structural frame. The skin of the wing is made in two parts and placed over the spars and ribs at top and bottom The primary objective is to optimize the wing thickness so several iterations are carried to reduce weight of wing including spar, rib, and skin. At the third iteration the optimize obtained. Then the skin is replaced by metallic to composite. (CFC), a composite laminate material for the wing panel effectively reduces the weight of the wing.weight reduction and lower productions costs are important goals for aircraft structural engineers and researchers. The use of advanced composite structures has increased to realize these goals 2.3 Wing Model The model consists of a subsonic aircraft wing.the various structural components are top and bottom panels, seven ribs and front and rear spars. To study the effects of composite laminate when compared to conventional material on wing structures, the panels were modeled as orthotropic CFC laminates and remaining components were modeled as isotropic material. The orthotropic materials properties are given in table.1 and the material properties of isotropic are given in table Analysis Method MSC-Nastran is a general purpose fem package for numerically solving a wide variety of problems. In this experimental analysis the wing model was first generated in catiav-5 and then the model is imported to hyper mesh for generating mesh and then the mesh model is further allowed to run in the Nastran software and by adding material properties in pastran software and further analysis results are obtained. III. Results And Discussion The static analysis of the air craft wing has been done using the pre and post processing of finite element model using Hyper mesh and solving in MSC/Nastran. The total weight of the aircraft wing made of the conventional material was seen to be25.85kg while that replaced with CFC weighed only13.55kg.hence the replacement of aluminum alloy by CFC reduces the total aircraft of the wing by 52.96% there by reducing the total weight of the aircraft tremendously MATERIAL PROPERTY MOD.OF ELASTICITY MASS DENSITY IV. Figures And Tables Table 1: Material Properties of Al. Alloy ALLUMINIUM 7000 mpa 2823 kg/m3 POISSON S RATIO 0.35 TENSILE STRENGTH 460 Table 2: following isotropic composite properties with symmetric balanced layups are shown Table 3: Lodes acting on wing station No. of layers 12 Thickness=(.12*12) 1.44mm Elastic modulus Elastic modulus Poisons ratio Shear modulus 5000 Tension stress limit N/mm2 Tension stress limit 22 60N/mm2 Shear stress limit 36N/mm2 Bending shear stress limit 80N/mm2 13 Page
3 Wing station no Aerodynamic loads in newton Table 4: Comparison of share force bending moment and twisting moment for the following given lodes Station Load(N) Shear force(n) Bending moment(nmm) Twisting number moment(n-mm) E E E E+07 Table 5: Maximum value of FE stress for aluminum material Wing component FE Stress in (N/mm2) Front spar 373 Rear spar 452 Top skin 412 Bottom skin 202 Ribs 202 Root rib 373 SL.No. 1 2 COMPONENT TOP BOTTOM Table 6: Reserve Factors at Ultimate Loads for composite wing skin MATERIAL. SPECIFICATION CFC CFC TYPE OF Stress/STRAIN Max Principal Stress Minimum principal Stress Max shear stress Major Principal Strain Minor principal strain DEVELOPED STRAIN ( s)/stress(mpa) ALLOW STRAIN ( s) RESERVE FACTOR Failure index Max Principal Stress Minimum principal Stress Max shear stress REMARKS Failure Index<1 Major Principal Page
4 Strain Minor principal strain Failure index Failure Index<1 Table 7: Comparison of weight reduction between CFC and aluminium alloy METALLIC COMPONENT Volume (mm3) Density(Kg/mm3) Mass kg Bottom skin E Top skin E COMPOSITE COMPONENT Volume(mm3) Density(kg/mm3) Mass kg Bottom skin E Top skin E TOTAL WEIGHT SAVING Mass(kg)-metallic Mass(kg)- composite Weight saving(kg) Bottom skin Top skin %wt. saving Figure 1: Wing Model Figure 2: Station diagram of the wing Figure 3: Wing shear force diagram 15 Page
5 Figure 4: Wing bending moment diagram Figure 5: Wing twisting moment diagram Figure 6: wing model in hyper mesh The combined wing was then analyzed using the MSc Nastran software to obtain the max. value of stress. V. Conclusion Since preliminary design of the wing structures carried out as per the industrial practices for the given applied loads by iteration process and we carried out 3 iterations for metallic structure and at iteration 3 we got the optimum structure and in iteration 4 the metallic wing skin, bottom and top is replaced with CFC and we have seen there is a weight saving of 52% as still there is a scope for weight reduction of this wing structure by replacing the metallic ribs and spars by composites. This is consider for the future scope of the project References [1] Numerical Analysis Of Carbon Fiber Reinforced Aircraft wing by SanyaMariaGomez [2] Air frame structural design by MICHAELCHUN-YUNG NIU [3] Topology Optimization of Aircraft Fuselage Structure by MuniyasamyK alanchiam and BaskarMannai [4] Finite Element Analysis of aircraft wing using composite structure by Dr.R.Rajappan,V.Pugazhenthi [5] Finite Element ModellingAnd Analysis Of Skin Panel Based On The Fiber Orientation And Stacking Sequence by Dr.R.Rajappan,Dr.S.Sundararaj and V.Pugazhenthi [6] Hybrid Wing-Body Pressurized Fuselage and Bulkhead,Design and Optimization by VivekMukhopadhyay 16 Page
STRUCTURAL DESIGN ON WING OF A SMALL SCALE WIG VEHICLE WITH CARBON/EPOXY AND FOAM SANDWICH COMPOSITE STRUCTURE
16 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS STRUCTURAL DESIGN ON WING OF A SMALL SCALE WIG VEHICLE WITH CARBON/EPOXY AND FOAM SANDWICH COMPOSITE STRUCTURE C. Kong*, H. Park*, Y. Kim* and K. Kang**
More informationSTRUCTURAL DESIGN OF DELTA WINGS OF AN EXECUTIVE SUPERSONIC AIRPLANE
STRUCTURAL DESIGN OF DELTA WINGS OF AN EXECUTIVE SUPERSONIC AIRPLANE João Marcelo de Castro Monteiro, jomakamon@gmail.com Flavio Luiz de Silva Bussamra, flaviobu@ita.br Instituto Tecnológico de Aeronáutica
More informationStress Analysis and Weight Optimization of a Wing Box Structure Subjected To Flight Loads
The International Journal Of Engineering And Science (IJES) Volume 3 Issue 1 Pages 33-40 2014 ISSN(e): 2319 1813 ISSN(p): 2319 1805 Stress Analysis and Weight Optimization of a Wing Box Structure Subjected
More informationDESIGN AND FINITE ELEMENT ANALYSIS OF AIRCRAFT WING USING RIBS AND SPARS
DESIGN AND FINITE ELEMENT ANALYSIS OF AIRCRAFT WING USING RIBS AND SPARS Sivarama Prasad Peruru 1, Suman Babu Abbisetti 2 1M.tech, student, mechanical enginnering Aditya Engineering College, Surampalem
More informationBearing and Delamination Failure Analysis of Pin Loaded Composite Laminates
Volume 6, No. 2, February 217 1 Bearing and Delamination Failure Analysis of Pin Loaded Composite Laminates V. Dinesh Babu, Professor, Nehru Institute of Engineering and Technology, Coimbatore T. Sivagangai,
More informationTHE CFRP SAILPLANE WING SEGMENTS MANUFACTURED BY FILAMENT PLACEMENT
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES THE CFRP SAILPLANE WING SEGMENTS MANUFACTURED BY FILAMENT PLACEMENT Michal Mališ*, Tomáš Urík*, Ondřej Uher** * Brno University of Technology,
More informationSeoul National University, San 56-1, Shillim-Dong, Kwanak-Gu, Seoul, Korea,
18 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS DEVELOPMENT OF CFRP PRECISION GANTRY BEAMS FOR 11 TH GENERATION LCD PANEL MANUFACTURING B. Bhandari 1, G.Y. Lee 1, D.S. Choi 2, J.H. Kim 2 and S.H.
More informationFinite Element Analysis of Flat Joints in Metallic Honeycomb Sandwich Beams
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) ISSN: 2278-1684 Volume 3, Issue 2 (Sep-Oct. 2012), PP 06-12 Finite Element Analysis of Flat Joints in Metallic Honeycomb Sandwich Beams Nishi
More informationStructural design of spars for 100-m biplane wind turbine blades
Structural design of spars for 100-m biplane wind turbine blades Perry M. Johnson & Richard E. Wirz Wirz Research Group, Energy Innovation Laboratory Department of Mechanical and Aerospace Engineering
More informationDEVELOPMENT OF GEODESIC COMPOSITE AIRCRAFT STRUCTURES
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES DEVELOPMENT OF GEODESIC COMPOSITE AIRCRAFT STRUCTURES V.V. Vasiliev, A.F. Razin Central Research Institute of Special Machinery vvvas@dol.ru Keywords:
More informationFlexural Behavior of Sandwich Composite Panels Under 4-Point Loading
International Journal of Materials Science ISSN 0973-4589 Volume 11, Number 1 (2016), pp. 47-55 Research India Publications http://www.ripublication.com Flexural Behavior of Sandwich Composite Panels Under
More informationINTERNATIONAL JOURNAL OF CIVIL AND STRUCTURAL ENGINEERING Volume 2, No 2, 2011
INTERNATIONAL JOURNAL OF CIVIL AND STRUCTURAL ENGINEERING Volume 2, No 2, 2011 Copyright 2010 All rights reserved Integrated Publishing services Research article ISSN 0976 4399 Nonlinear Seismic Behavior
More informationBEHAVIOR OF REINFORCED CONCRETE BEAM WITH OPENING
International Journal of Civil Engineering and Technology (IJCIET) Volume 8, Issue 7, July 2017, pp. 581 593, Article ID: IJCIET_08_07_062 Available online at http:// http://www.iaeme.com/ijciet/issues.asp?jtype=ijciet&vtype=8&itype=7
More informationDesign and Analysis of a Connecting Rod
Design and Analysis of a Connecting Rod Sebastian Antony, Arjun A., Shinos T. K B.Tech. Mechanical Dept. Muthoot Institute of Technology and Science Ernakulam, India Abstract The main function of a connecting
More informationAdvantages of Composite Materials in Aircraft Structures
Advantages of Composite Materials in Aircraft Structures Muniyasamy Kalanchiam, and Moorthy Chinnasamy Abstract In the competitive environment of aircraft industries it becomes absolutely necessary to
More informationAnalysis of Composite Structure Using HM12.0/Radioss
Analysis of Composite Structure Using HM12.0/Radioss Anil M.Sutar Design Engineer Citec Engineering India Pvt. Ltd. Yerwada, Pune 411 006 anil.sutar@citec.com Abbreviations: FE- Finite Element, GRP-Glass
More informationNonlinear Analysis of Reinforced Concrete Column with ANSYS
Nonlinear Analysis of Reinforced Concrete Column with ANSYS V. S. Pawar 1, P. M. Pawar 2 1P.G. Student, Dept. Of civil Engineering, SVERI s College of Engineering Pandharpur, Maharashtra, India 2Professor,
More informationDesign and Testing of Wing Leading Edge of a Light Transport Aircraft
Design and Testing of Wing Leading Edge of a Light Transport Aircraft Stanley C. Salem, Kotresh M. Gaddikeri, MNN Gowda, Ramesh Sundaram Advanced Composites Division, National Aerospace Laboratories, Bangalore,
More informationE APPENDIX. The following problems are intended for solution using finite element. Problems for Computer Solution E.1 CHAPTER 3
E APPENDIX Problems for Computer Solution The following problems are intended for solution using finite element analysis software. In general, the problems associated with Chapters 3, 4, and 9 can be solved
More informationMECHANICAL PROPERTIES OF TRIAXIAL BRAIDED CARBON/EPOXY COMPOSITES
MECHANICAL PROPERTIES OF TRIAXIAL BRAIDED CARBON/EPOXY COMPOSITES C. L. Bowman 1, G. D. Roberts 1, M. S. Braley 2, M. Xie 3 & M. J. Booker 4 1 NASA Glenn Research Center, Cleveland OH 44135 2 A&P Technology,
More informationProperties in Shear. Figure 7c. Figure 7b. Figure 7a
Properties in Shear Shear stress plays important role in failure of ductile materials as they resist to normal stress by undergoing large plastic deformations, but actually fail by rupturing under shear
More informationStructural Design of a Containership Approximately 3100 TEU According to the Concept of General Ship Design B-178
Structural Design of a Containership Approximately 3100 TEU According to the Concept of General Ship Design B-178 W.Souadji, Zbigniew Sekulski, B.Hamoudi 1 Abstract The design developed in this work is
More informationAn Approach to Preliminary Design and Analysis
48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 23-26 April 2007, Honolulu, Hawaii AIAA 2007-2176 An Approach to Preliminary Design and Analysis Craig Collier 1, Phil
More informationPart 4 MECHANICAL PROPERTIES
Part 4 MECHANICAL PROPERTIES Fiber Composite Materials M. S. Ahmadi 192 TENSILE PROPERTIES Tensile properties, such as tensile strength, tensile modulus, and Poisson s ratio of flat composite laminates,
More informationVibration Analysis of Propeller Shaft Using FEM.
Vibration Analysis of Propeller Shaft Using FEM. 1 Akshay G. Khande, 2 Shreyash A. Sable, 3 Vaibhav R. Bidwai, 4 Chandrasekhar B. Aru, 5 Brahmanand S.Jadhav 12345 Mechanical Engineering Department, Babasahebh
More informationC-130 HERCULES COMPOSITE FLAPS FATIGUE TEST PROGRAM
C-130 HERCULES COMPOSITE FLAPS FATIGUE TEST PROGRAM J. Ayling Hawker de Havilland Pty Ltd 361 Milperra Road, Bankstown, New South Wales, 2200, Australia SUMMARY: The C130 Fatigue Test Program was a task
More informationCOMPARATIVE STUDY ON NORMAL AND SKEW BRIDGE OF PSC BOX GIRDER
IJRET: International Journal of Research in Engineering and Technology eissn: 2319-1163 pissn: 2321-738 COMPARATIVE STUDY ON NORMAL AND SKEW BRIDGE OF PSC BOX GIRDER Pranathi Reddy 1, Karuna S 2 1 Post
More informationA design methodology using bi-angle ply laminates made from NCF carbon fiber materials
18 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS A design methodology using bi-angle ply laminates made from NCF carbon fiber materials 1 - General vision of NCF Th. Massard *1, R. Harry 2, Ph. Sanial
More informationDesign of Integrated Super Bracket for Heavy Commercial vehicles
ISSN 2395-1621 Design of Integrated Super Bracket for Heavy Commercial vehicles #1 Amar Vhanshetti, #2 Nitin S. Chavan 1 amarvhanshetti@yahoo.com 2 nsc_04@rediffmail.com #12 Dept. of Mechanical Engineering
More informationTorsional evaluation of Tapered Composite Cone using Finite Element Analysis
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 7, Issue 3 (Jul. - Aug. 2013), PP 29-36 Torsional evaluation of Tapered Composite Cone using Finite
More informationDesign & Analysis of Mono Composite Leaf Spring
Design & Analysis of Mono Composite Leaf Spring R D V Prasad 1, R.Sai Srinu 2, P.Venkata rao 3 Asst.Prof 1, M.Tech Student 2, Asst.Prof 3 1 Asst.Professor Department of Mechanical Engineering, Bits Vizag,
More informationFE Review Mechanics of Materials
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 1. T he element is subjected to the plane stress condition shown. a-x = - 140 M Pa a- y = 205 M Pa Txy = 100 M Pa What is t
More informationDynamics of Composite Beam with Transverse Non-Propagating Open Crack
Dynamics of Composite Beam with Transverse Non-Propagating Open Crack Arjun S. Menon 1 and Glory Joseph 2 1 M. Tech Student, Cochin University Of Science And Technology, Cochin,India arjunsmenon44@gmail.com
More informationthat maximum deformation occurs at the centre of crankpin neck surface and maximum stress appears at fillet areas of
Structural Static Analysis of Crankshaft B. Mounika 1, Madhuri.R.P 2 1 P.G Student, Mechanical Engineering, Hindustan Institute of Technology and Science, Chennai, India 2 Assistant Professor, Mechanical
More informationDesign of a Composite Vibration Fixture for Testing Fuel Tank for Combat Vehicle Application
International NAFEMS Conference on Engineering Analysis, Modeling, Simulation and 3D-Printing (NAFEMS-3D) 2016 Design of a Composite Vibration Fixture for Testing Fuel Tank for Combat Vehicle Application
More informationDesign, Analysis and Optimization of Overhead Crane Girder
Design, Analysis and Optimization of Overhead Crane Girder Pratik R Patel 1, Bhargav J Patel 2, Vipul K Patel 3 1 M.E student in Mechanical Department, S K Patel Engineering College, Visnagar 2 Assistant
More informationAuto Pilot Controlled Flying Wing (UAV) For QRF (Quick Reaction Armed Forces)
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 12, Issue 6 Ver. II (Nov. - Dec. 2015), PP 43-47 www.iosrjournals.org Auto Pilot Controlled Flying
More informationI. INTRODUCTION. International Journal of Engineering Innovation & Research Volume 4, Issue 4, ISSN:
Experimental and FEA Comparison of Cold Formed Stainless Steel and Aluminium Alloy Having Perforation of Various Combinations Subjected to Buckling Load Prof. I. G. Bhavi Associate Prof., Department of
More informationStudy of Darwin guidelines for non-compact and slender steel girders with web openings
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 12, Issue 5 Ver. I (Sep. - Oct. 2015), PP 72-85 www.iosrjournals.org Study of Darwin guidelines
More informationSTUDY ON DESIGN AND STATIC ANALYSIS OF PISTON HEAD
STUDY ON DESIGN AND STATIC ANALYSIS OF PISTON HEAD Amitanand B Suralikerimath 1, Yallanagouda I Ninganagoudar 2, C.M Veerendrakumar 3 1 Student, Department of Mechanical Engineering, Basaveshwar Engineering
More informationSimulation of Steel and Composite Leaf Spring by Varying Thickness
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 12, Issue 4 Ver. III (Jul. - Aug. 2015), PP 99-103 www.iosrjournals.org Simulation of Steel and
More informationANALYSIS OF FRP COMPOSITE CYLINDERS
Int. J. Mech. Eng. & Rob. Res. 2012 D Gopichand and T N Charyulu, 2012 Research Paper ISSN 2278 0149 www.ijmerr.com Vol. 1, No. 3, October 2012 2012 IJMERR. All Rights Reserved ANALYSIS OF FRP COMPOSITE
More informationSAMPE Brazil Conference Presentation prepared by: M. Alexander Roth, Dr.-Ing.
Experimental and numerical analysis under axial and bending loading of hollow and foam filled A-profiles as stiffener concept for FRP structures for the aerospace industry SAMPE Brazil Conference 2014
More informationNonlinear Finite Element Modeling & Simulation
Full-Scale Structural and Nonstructural Building System Performance during Earthquakes & Post-Earthquake Fire A Joint Venture between Academe, Industry and Government Nonlinear Finite Element Modeling
More informationScientific Seminar Design of Steel and Timber Structures SPbU, May 21, 2015
Riga Technical University Institute of Structural Engineering and Reconstruction Scientific Seminar The research leading to these results has received the funding from Latvia state research programme under
More informationANALYSIS AND COMPARISON... Continued /rom preceding page
Analysis ANALYSIS AND COMPARISON... Continued /rom preceding page 8.18 = 8.18 = B x 63 B x 216 b x (6 1.5)3 b X 91.5 18 B 7.593 b. Now since b = B minus the web or.5 inches, we have 8.18 = 18B 7.593B +
More informationIntroduction to Aerospace Engineering
Introduction to Aerospace Engineering Lecture slides Challenge the future 1 15-12-2012 Introduction to Aerospace Engineering 13 & 14. Materials & Exploring the limits J. Sinke Delft University of Technology
More information5.4 Analysis for Torsion
5.4 Analysis for Torsion This section covers the following topics. Stresses in an Uncracked Beam Crack Pattern Under Pure Torsion Components of Resistance for Pure Torsion Modes of Failure Effect of Prestressing
More informationSCHOOL OF ENGINEERING BENG (HONS) MECHANICAL ENGINEERING SEMESTER /2016 STRUCTURES AND MATERIALS MODULE NO: AME6002
SCHOOL OF ENGINEERING TW52 BENG (HONS) MECHANICAL ENGINEERING SEMESTER 1-2015/2016 STRUCTURES AND MATERIALS MODULE NO: AME6002 Date: Monday 11 January 2016 Time: 10.00 1.00pm INSTRUCTIONS TO CANDIDATES:
More informationDesign and Analysis of Antenna Reflector Using Composite Materials
Design and Analysis of Antenna Reflector Using Composite Materials Mithunkumar C.N, Venkateshmurthy Mechanical department, NMAMIT, Nitte, India. Abstract: An Antenna is basically a dish-shaped device of
More informationMECHANICAL CHARACTERIZATION OF SANDWICH STRUCTURE COMPRISED OF GLASS FIBER REINFORCED CORE: PART 1
Composites in Construction 2005 Third International Conference Lyon, France, July 11 13, 2005 MECHANICAL CHARACTERIZATION OF SANDWICH STRCTRE COMPRISED OF GLASS FIBER REINFORCED CORE: PART 1 S.V. Rocca
More informationComparative Study of Automotive Bumper with Different Materials for Passenger and Pedestrian Safety
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 11, Issue 4 Ver. III (Jul- Aug. 2014), PP 60-64 Comparative Study of Automotive Bumper with Different
More informationTodd F. Shupe Associate Professor School of Renewable Natural Resources Louisiana State University AgCenter Baton Rouge, LA 70803
FINITE ELEMENT ANALYSES OF WOOD LAMINATED COMPOSITE POLES 1 Cheng Piao Postdoctoral Research Associate USDA Forest Service Forest Products Laboratory Madison, WI 53726 Todd F. Shupe Associate Professor
More informationVibration Analysis of an Ocean Current Turbine Blade
International Journal of Scientific & Engineering Research, Volume 3, Issue 0, October-202 ISSN 2229-55 Vibration Analysis of an Ocean Current Turbine Blade M. Imran and S.Badshah 2 Department of Mechanical
More informationNUMERICAL STUDY ON STRESS ANALYSIS OF CURVED BEAMS
NUMERICAL STUDY ON STRESS ANALYSIS OF CURVED BEAMS Numerical Study on Stress Analysis of Curved Beams, D.Bharadwaj, A.Purushotham, Journal D.Bharadwaj 1, A.Purushotham 2 Volume 6, Issue 7, July (2015),
More informationNon Linear Analysis of Composite Beam Slab Junction with Shear Connectors using Ansys.16
International Journal of Engineering Science Invention ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 Volume 5 Issue 4 April 2016 PP.22-29 Non Linear Analysis of Composite Beam Slab Junction with Shear
More informationCOMPOSITE LANDING GEAR COMPONENTS FOR AEROSPACE APPLICATIONS
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES COMPOSITE LANDING GEAR COMPONENTS FOR AEROSPACE APPLICATIONS H.G.S.J. Thuis National Aerospace Laboratory NLR Keywords: Composites, Resin Transfer
More informationA new metamodel for reinforced panels under compressive loads and its application to the fuselage conception
11(2014) 223 244 A new metamodel for reinforced panels under compressive loads and its application to the fuselage conception Abstract This work presents a new metamodel for reinforced panels under compressive
More informationStrength Study on Castellated Beam
Strength Study on Castellated Beam 1 B. Anupriya 2 Dr. K. Jagadeesan 1 Assistant Professor Department of Civil Engineering Arasu Engineering College, Kumbakonam, Tamilnadu, India 2 Professor Department
More informationDESIGN AND ANALYSIS OF COMPOSITE DRIVE SHAFT
DESIGN AND ANALYSIS OF COMPOSITE DRIVE SHAFT V. S. BHAJANTRI 1, S. C. BAJANTRI 2, A. M. SHINDOLKAR 3, S. S. AMARAPURE 4 1 Assistant Professor, Dept. Of Mech. Engg., SCET, Belgaum-591156 2 Assistant Professor,
More informationImpact Analysis of Density Graded E-Glass Composite Laminate
Impact Analysis of Density Graded E-Glass Composite Laminate Sedulingam Kandaswamy 1, Deepthi K R 2 1PG Scholar, 2 Assistant Professor 1, 2 Dept. of Mechanical Engineering, New Horizon College of Engineering,
More informationComparison of Energy Absorption Characteristics of Thermoplastic Composites, Steel and Aluminum in High-Speed Crush Testing of U-Beams
Comparison of Energy Absorption Characteristics of Thermoplastic Composites, Steel and Aluminum in High-Speed Crush Testing of U-Beams CELANESE ENGINEERED MATERIALS Michael Ruby October, 2013 1 Overview
More informationModal Analysis of Composite Sandwich Panel
International Journal of Current Engineering and Technology E-ISSN 2277 4106, P-ISSN 2347 5161 2016 INPRESSCO, All Rights Reserved Available at http://inpressco.com/category/ijcet Research Article G.D.Shrigandhi
More informationDetermination of Engineering Properties and Modeling of Wood I-Joists
Determination of Engineering Properties and Modeling of Wood I-Joists Summary Jean-Frédéric Grandmont, ing.jr. Ph.D Candidate Université Laval Québec, Canada Constance Thivierge, ing. B.Sc.A Industry Advisor
More informationOn Finite Element Analysis of Steel and RC Beams : Performance of Different Elements
On Finite Element Analysis of Steel and RC Beams : Performance of Different Elements Biswanath Charan 1, Pijush Topdar 2 1 (M-Tech student, Dept. of Civil Engg NIT Durgapu,India) 2 (Assistant Professor,
More informationStructural and vibration analysis of delaminated composite beams
ISSN (e): 2250 3005 Vol, 04 Issue, 10 October 2014 International Journal of Computational Engineering Research (IJCER) Structural and vibration analysis of delaminated composite beams 1 Narra.Sowjanya,
More informationStudy of Buckling Behavior of Beam and Column
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 11, Issue 4 Ver. I (Jul- Aug. 2014), PP 36-40 Study of Buckling Behavior of Beam and Column 1 Rekha
More informationANALYSIS IMPLEMENTATION, VERIFICATION, VALIDATION AND PERFORMANCE OF A STRUCTURALLY- INTEGRATED TPS CONCEPT
ANALYSIS IMPLEMENTATION, VERIFICATION, VALIDATION AND PERFORMANCE OF A STRUCTURALLY- INTEGRATED TPS CONCEPT James J. Ainsworth, Craig S. Collier, Phil W. Yarrington, Ryan C. Lucking Collier Research Corp.
More informationBehavior of Concrete-Filled FRP Tubes Under Bending, Axial Loads, and Combined Loading. Amir Fam, Bart Flisak and Sami Rizkalla
Behavior of Concrete-Filled FRP Tubes Under Bending, Axial Loads, and Combined Loading Amir Fam, Bart Flisak and Sami Rizkalla ABSTRACT Innovative hybrid systems such as the concrete-filled fiber reinforced
More informationStructural Design of Pergola with Airfoil Louvers
International Journal of Advanced Structures and Geotechnical Engineering ISSN 2319-5347, Vol. 04, No. 03, July 2015 Structural Design of Pergola with Airfoil Louvers MUHAMMAD TAYYAB NAQASH Aluminium TechnologyAauxiliary
More informationPORTAL FRAMES 1.0 INTRODUCTION
36 PORTAL FRAMES 1.0 INTRODUCTION The basic structural form of portal frames was developed during the Second World War, driven by the need to achieve the low - cost building envelope. Now they are the
More informationStructural strength of work boats and high speed crafts with floating frames
Structural strength of work boats and high speed crafts with floating frames JON E N G L U N D j o n e n g 9 5 @ k t h. s e M a s t e r T h e s i s, K T H C e n t r e f o r N a v a l A r c h i t e c t
More informationOptimization of Aluminum Stressed Skin Panels in Offshore Applications
Materials 2014, 7, 6811-6831; doi:10.3390/ma7096811 Article OPEN ACCESS materials ISSN 1996-1944 www.mdpi.com/journal/materials Optimization of Aluminum Stressed Skin Panels in Offshore Applications Dianne
More informationDETERMINATION OF FAILURE STRENGTH OF CURVED PLATE WELD JOINT USING FINITE ELEMENT ANALYSIS
Int. J. Mech. Eng. & Rob. Res. 2012 Chetan S Baviskar et al., 2012 Research Paper ISSN 2278 0149 www.ijmerr.com Vol. 1, No. 3, October 2012 2012 IJMERR. All Rights Reserved DETERMINATION OF FAILURE STRENGTH
More informationBehaviour of Concrete Filled Rectangular Steel Tube Column
IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) ISSN: 2278-1684 Volume 4, Issue 2 (Nov. - Dec. 2012), PP 46-52 Behaviour of Concrete Filled Rectangular Steel Tube Column Anil Kumar Patidar
More informationINTERNATIONAL JOURNAL OF CIVIL AND STRUCTURAL ENGINEERING Volume 3, No 1, 2012
INTERNATIONAL JOURNAL OF CIVIL AND STRUCTURAL ENGINEERING Volume 3, No 1, 2012 Copyright by the authors - Licensee IPA- Under Creative Commons license 3.0 Research article ISSN 0976 4399 Finite element
More informationCharacterization of Mechanical Properties of SiC/Ti-6Al-4V Metal Matrix Composite (MMC) Using Finite Element Method
American Journal of Materials Science 2015, 5(3C): 7-11 DOI: 10.5923/c.materials.201502.02 Characterization of Mechanical Properties of SiC/Ti-6Al-4V Metal Matrix Composite (MMC) Using Finite Element Method
More informationAn example of finite element modelling of progressive collapse
COST Action TU0601 Robustness of Structures 2nd and 3rd of March 2009 Coimbra, Portugal An example of finite element modelling of progressive collapse Leslaw KWASNIEWSKI Marian A. GIZEJOWSKI Faculty of
More informationMEASUREMENT OF THE MECHANICAL PROPERTIES OF A CARBON REINFORCED BISMALEIMIDE OVER A WIDE RANGE OF TEMPERATURES
Revista da Associação Portuguesa de Análise Experimental de Tensões ISSN 66-778 MEASUREMENT OF THE MECHANICAL PROPERTIES OF A CARBON REINFORCED BISMALEIMIDE OVER A WIDE RANGE OF TEMPERATURES L. F. M. da
More informationDesign Optimization Using HyperSizer
Design Optimization Using HyperSizer Craig Collier, Phil Yarrington, and Mark Pickenheim Collier Research Corporation 2101 Executive Dr. 6 th floor Tower Box 72 Hampton, Virginia 23666 collier-research.com
More informationDYNAMIC RESPONSE ANALYSIS OF THE RAMA 9 BRIDGE EXPANSION JOINT DUE TO RUNNING VEHICLE
DYNAMIC RESPONSE ANALYSIS OF THE RAMA 9 BRIDGE EXPANSION JOINT DUE TO RUNNING VEHICLE Tanan Chub-uppakarn 1, Adison Owatsiriwong 2* 1 Department of Civil Engineering, Faculty of Engineering, Prince of
More informationParametric Study of Continuous Concrete Beam Prestressed with External Tendon
Parametric Study of Continuous Concrete Beam Prestressed with External Tendon Assistant Professor, College of Engineering, Diyala University, Iraq ABSTRACT This paper presents the results of a parametric
More informationThe Behavior of Tensile Fabric Membrane Structure
The Behavior of Tensile Fabric Membrane Structure Attarwala Shehzad I 1, Ankit Agrawal 2, Ar Parimal Jhuvar 3 1P.G. Student, Parul Institute of Technology, Waghodia 2Assistant Professor, Parul Institute
More informationStudy of Shear Behavior of RC Beams: Non Linear Analysis
Study of Shear Behavior of RC Beams: Non Linear Analysis 3477 Study of Shear Behavior of RC Beams: Non Linear Analysis Umer Farooq and K.S. Bedi1 Abstract Shear Failure of reinforced concrete beam more
More informationNUMERICAL ANALYSIS OF REINFORCED LIGHTWEIGHT AGGREGATE CONCRETE HOLLOW CORE SLABS
NUMERICAL ANALYSIS OF REINFORCED LIGHTWEIGHT AGGREGATE CONCRETE HOLLOW CORE SLABS Adel A. Al-Azzawi and Basma M. Abdul Al-Aziz Department of Civil Engineering, Factually of Engineering, Al-Nahrain University,
More informationComparative Study On Seismic Behaviour Of Steel Knee Braced Frame With Eccentric Braced Frame
Comparative Study On Seismic Behaviour Of Steel Knee Braced Frame With Eccentric Braced Frame Anitha M 1, Divya K.K 2 1 M.Tech Scholar, Department of Civil Engineering, SN Gurukulam College of Engineering,
More informationThe Flexural Properties of Glass Fabric/Epoxy -Rigid Polyurethane Foam Core Sandwich Composites at Different Span to Depth Ratios and Densities
Proc. of the Intl. Conf. on Advances In Engineering And Technology - ICAET-214 ISBN: 978-1-63248-28-6 doi: 1.15224/ 978-1-63248-28-6-3-87 The Flexural Properties of Glass Fabric/Epoxy -Rigid Polyurethane
More informationBehavior and Analysis of Horizontally Curved Composite Steel Girder Bridge System
e-issn: 2278-1684, p-issn: 232-334X. PP 45-52 Behavior and Analysis of Horizontally Curved Composite Steel Girder Bridge System Gourav Gajrani 1, Dr. L. M. Gupta 2 1,2 (Department of App. Mechanics, VNIT,
More informationApplication of Tensioned CFRP Strip Method to an Existing Bridge
SP-230 66 Application of Tensioned CFRP Strip Method to an Existing Bridge by A. Tateishi, A. Kobayashi, Y. Hamada, T. Takahashi, and H. Yasumori Synop nopsis: s: Tensioned carbon fiber reinforced polymer
More informationSTUDY OF CASTELLATED BEAM USING STIFFENERS: A REVIEW
STUDY OF CASTELLATED BEAM USING STIFFENERS: A REVIEW Siddheshwari. A. Patil 1, Popat. D. Kumbhar 2 1 PG Scholar, Department of Civil Engineering, RIT Rajaramnagar, Maharashtra, India 2 Associate Professor,
More informationStrength Design of Reinforced Concrete Structures
Chapter 6 Strength Design of Reinforced Concrete Structures 6.1 Analysis and Design General Considerations 6.1.1 Convention and Notation Unless otherwise explicitly stated, the following units shall be
More informationChapter 3: Torsion. Chapter 4: Shear and Moment Diagram. Chapter 5: Stresses In beams
Chapter 3: Torsion Chapter 4: Shear and Moment Diagram Chapter 5: Stresses In beams Torsion Torsion or Torque, T, put simply, is referred to as a twisting moment. θ The derived formulas are: Where: Torsional
More informationInternational Journal of Scientific & Engineering Research, Volume 6, Issue 3, March ISSN
International Journal of Scientific & Engineering Research, Volume 6, Issue 3, March-2015 153 Frequency response analysis of a Clamped Composite Plate with a Central Circular Cutout using ANSYS Kolaventi.sasikumar,
More informationEndurance testing and FE analysis of four wheeler automobile stabilizer bar
Endurance testing and FE analysis of four wheeler automobile stabilizer bar P.Senapathi, S.Shamasundar, G. Venugopala Rao and B.M.Sachin ProSIM R&D Center,Bangalore. Krishna Srinivas, N.Dasari, Cheryl
More informationStudy of Fatigue Behavior of Composite Materials with the Basis of Polyphenylene Sulfide (PPS) Reinforced with Glass Fiber and Carbon
International Journal of Engineering and Technology Volume 3 No. 4, April, 213 Study of Fatigue Behavior of Composite Materials with the Basis of Polyphenylene Sulfide (PPS) Reinforced with Glass Fiber
More informationEffect of Sheet Thickness and Type of Alloys on the Springback Phenomenon for Cylindrical Die
AMERICAN JOURNAL OF SCIENTIFIC AND INDUSTRIAL RESEARCH 01, Science Huβ, http://www.scihub.org/ajsir ISSN: 153-69X, doi:10.551/ajsir.01.3.6.80.86 Effect of Sheet Thickness and Type of Alloys on the Springback
More informationDESIGN METHODOLOGY FOR BUCKLING OF THIN-WALLED LAMINATED COMPOSITE BEAMS
DESIGN METHODOLOGY FOR BUCKLING OF THIN-WALLED LAMINATED COMPOSITE BEAMS Lawrence W. Rehfield and Ulrich Mueller Department of Mechanical and Aeronautical Engineering University of California, Davis Davis,
More informationINNOVATIVE DESIGN OF THE COMPOSITE LATTICE FRAME OF A SPACECRAFT SOLAR ARRAY
INNOVATIVE DESIGN OF THE COMPOSITE LATTICE FRAME OF A SPACECRAFT SOLAR ARRAY E. V. Morozov 1 and A.V. Lopatin 2 1 School of Aerospace, Civil & Mechanical Engineering, University of New South Wales, University
More informationUpgrading the shear strength of non-ductile reinforced concrete frame connections using FRP overlay systems
Upgrading the shear strength of non-ductile reinforced concrete frame connections using FRP overlay systems Mohamad J. Terro Associate Professor. Civil Engineering Department, Kuwait University. Sameer
More informationBEHAVIOR OF INFILL MASONRY WALLS STRENGTHENED WITH FRP MATERIALS
BEHAVIOR OF INFILL MASONRY WALLS STRENGTHENED WITH FRP MATERIALS D.S. Lunn 1,2, V. Hariharan 1, G. Lucier 1, S.H. Rizkalla 1, and Z. Smith 3 1 North Carolina State University, Constructed Facilities Laboratory,
More information